Abstract
A thrust vectoring device contains four or more vanes placed in a cascade over the exit of a nozzle to vector thrust and regulate the discharge throat area. A rod is included in the system to control the pivoting of each of the vanes, which may be turned selectively using one or more actuators. It has critical functional advantages in military, compassionate, and salvage missions, just as broad flight. In this paper, a Convergent-Divergent (C-D) spout with different vectoring and non-vectoring are used to accomplish supersonic stream, and by using the secondary injections thrust vector control (SITVC) to achieve the most extreme changes in pressure or velocity and Mach number. The C-D nozzle with various cases, i.e., mechanically deflects the divergent section downward by 10°, 15° and 20° angles over an axis, keeping the same boundary condition are designed in CATIA software. CFD analysis is carried out to determine the pressure, velocity, Mach number for various cases C-D nozzle with and analyzing the C-D nozzle with various cases of vectoring and non-vectoring in ANSYS software.
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